CN103010458A - Vectored thrust type unmanned aerial vehicle - Google Patents
Vectored thrust type unmanned aerial vehicle Download PDFInfo
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- CN103010458A CN103010458A CN2012105582245A CN201210558224A CN103010458A CN 103010458 A CN103010458 A CN 103010458A CN 2012105582245 A CN2012105582245 A CN 2012105582245A CN 201210558224 A CN201210558224 A CN 201210558224A CN 103010458 A CN103010458 A CN 103010458A
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- unmanned plane
- vectored thrust
- fuselage
- jet pipe
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Abstract
The invention relates to a vectored thrust type unmanned aerial vehicle. The vehicle comprises propellers, a body, wings and empennages, wherein the propellers are coaxially mounted at the front end of a longitudinal shaft of the body; the wings are symmetrically mounted on two sides of the middle part of the body; the empennages are symmetrically mounted on two sides of the tail part of the body; a vectored thrust device is mounted at the tail part of the longitudinal shaft of the body, and comprises a motor and a spray pipe; the motor is mounted inside the body; and the front end of the spray pipe is connected with the motor, and the tail end of the spray pipe extends outside the tail end of the body. The vehicle has the advantages of scientific design, reasonable structure, strong controllability, quick taking-off and landing speed, good safety, small size, light weight and good maneuvering characteristic, can guarantee low-speed maneuvering flight in a state of high attack angle, can effectively improve the maneuverability, and can shorten the skating distance in the taking-off and landing process.
Description
Technical field
The invention belongs to the unmanned plane field, especially a kind of vectored thrust type unmanned plane.
Background technology
Act on thrust on the unmanned plane and be one size, directive amount are arranged, this amount is called as vector, and Thrust Vectoring Technology is exactly the direction by the yaw motor jet flow, thereby obtains the technology of additional manipulation moment.
At present, the operating flying angle of common unmanned plane is smaller, and the wing of unmanned plane and empennage can both produce enough lift in this state, can guarantee the normal flight of unmanned plane.But when the unmanned plane angle of attack increases gradually, the empennage of unmanned plane will be absorbed in the low energy wake flow of wing, may cause empennage stall, even make unmanned plane enter tailspin and cause crashing, at this moment, although motor operation is normal, also can't make unmanned plane maintenance balance and rest on aerial.
Find following correlation technique through retrieval:
Three-dimensional vector propulsion device for submersible (CN202226050U), comprise the thrust mechanism of primary mover, support, at least three group same structures and be distributed in the periphery of support, main shaft is by prime mover driven, main shaft and support normal-running fit, main shaft outer end pass behind the outer wall of support affixed with the inner bottom surface of rolling disc; Main shaft is hollow form, its inside transmission shaft that stretches through vertically, stretch out outside the inwall of main shaft and support the inner of transmission shaft, and link to each other with the thrust direction controller, the other end passes behind the interior end of rolling disc and the sun gear interlock, and this end is loaded on the outer bottom of rolling disc rotationally; Sun gear is in the rolling disc, the several blade spindles of normal-running fit in the rolling disc, and blade spindle passes blade gear interlock, and the blade gear links to each other with sun gear by Transmission, and it is affixed that blade spindle stretches out an end of the outer bottom of rolling disc and blade; In one week of turn disc, blade is around self axis rotation half cycle.The size of thrust of the present invention and direction can change arbitrarily in three dimensional space.
The engine installation (CN202226062U) of the empty dual-purpose unmanned plane of a kind of water, the unmanned plane closed fuselage inner end surface that engine installation is housed is connected with the sump support, fuel tank fixedly is housed in the sump support, fuel tank is connected to the single cylinder piston engine through oil pipe, the piston-engined output shaft engaging gear of single cylinder, the transmission shaft of gear transmission outside fuselage, end part of driving shaft is connected with the folding air screw, be provided with admission port and air extractor duct on the closed fuselage, they realize folding to closed fuselage by the air inlet and exhaust valve of intake and exhaust device, and the fuselage inner end surface also is connected with the dynamic lithium battery support.Technique effect of the present invention is: by the driven by motor screw rod, the rotation of screw rod drives the nut that is connected with air inlet valve and blow off valve, the effectively folding of control air inlet valve and blow off valve, achieve the single cylinder piston engine that needs air aloft when unmanned plane navigates by water and to obtain enough air and work, effectively avoid water to enter unmanned aerial vehicle body and affect navigation when navigating by water under water simultaneously.
Dual-autopilot flight controller for unmanned aerial vehicle (CN202226055U), be divided into main automatic Pilot control setup and backup automatic Pilot control setup, main automatic Pilot control setup normally is connected in the control circuit of unmanned plane, simultaneously by data transmission radio station and main earth station terminal called.Backup automatic Pilot control setup is controlled the power supply of main automatic Pilot control setup, backs up simultaneously the automatic Pilot control setup is in the physics disconnection that is subjected to switch control towards the signal line of each steering wheel state, only connects 1 tunnel task steering wheel or relay.The present invention will pass by singly, and the automatic Pilot control setup of cover replaces with two automatic Pilot control setups that overlap.The probability of two cover automatic Pilot control setups while et out of orders is very low, and when a cover automatic Pilot control setup et out of order, backup automatic Pilot control setup just can be taken over it and finish aerial mission.
Through contrast, the technology of above patent documentation and present patent application exists more different.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art part, a kind of design science, rational in infrastructure, controllability is strong, the speed of rising and falling is fast, manoevreability is good vectored thrust type unmanned plane are provided.
The present invention solves its technical matters and takes following technical scheme to realize:
A kind of vectored thrust type unmanned plane, comprise screw propeller, fuselage, wing and empennage, propeller coaxial is installed in the fuselage datum front end, the waist bilateral symmetry is installed wing, and the afterbody bilateral symmetry is equipped with empennage, it is characterized in that: described fuselage datum afterbody is equipped with a vectored thrust device, this vectored thrust device comprises electrical motor and jet pipe, described electrical motor is installed in fuselage interior, and the jet pipe front end connects electrical motor, and the jet pipe tail end stretches out the fuselage tail end.
And described jet pipe tail end is by jet pipe deflector control rotation angle.
And described wing rear side all is hinged with aileron.
Advantage of the present invention and good effect are:
1, this unmanned plane is installed the vectored thrust device at afterbody, the jet pipe of electrical motor is up and down deflection not only, can also deflection, thrust not only can provide the pitching moment of unmanned plane so, yawing moment can also be provided, can guarantee to do low speed, large angle of attack state maneuvering flight at unmanned plane, even the additional manipulation moment of utilizing thrust vectoring to provide when a few near failure of primary control surface is controlled the unmanned plane normal flight.
2, this unmanned plane adopts Thrust Vectoring Technology to improve the control efficiency of unmanned plane, make the air operated control face of unmanned plane, can greatly dwindle such as vertical fin and vertical tail, thereby alleviate the weight of unmanned plane, in addition, therefore the corner reflector that vertical fin and vertical tail form also dwindles, and the Stealth Fighter of unmanned plane also is improved.
3, this unmanned plane adopts Thrust Vectoring Technology, can control easy realization deboost, not only effectively promotes the manoevreability of unmanned plane, and can shorten the ground run distance of unmanned plane, makes unmanned plane have unprecedented STOL capability.
4, design science of the present invention, rational in infrastructure, controllability is strong, the speed of rising and falling is fast, safety good, can guarantee to do low speed, large angle of attack state maneuvering flight at unmanned plane, volume is little, quality is light, maneuvering performance is good, not only effectively promote the manoevreability of unmanned plane, and can shorten unmanned plane rise, the fall ground run distance of process.
Description of drawings
Fig. 1 is structural front view of the present invention (afterbody semi-sictional view);
Fig. 2 is the upward view (afterbody semi-sictional view) of Fig. 1.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing and by specific embodiment, and following examples are descriptive, are not determinate, can not limit protection scope of the present invention with this.
A kind of vectored thrust type unmanned plane, comprise screw propeller 1, fuselage 2, wing 3 and empennage 9, propeller coaxial is installed in the fuselage datum front end and drives control by the brushless motor that is installed in the fuselage, the waist bilateral symmetry is installed wing, the fuselage datum two sides of tail is symmetrically installed with empennage, and innovative point of the present invention is:
Described fuselage datum afterbody is coaxially installed with a vectored thrust device, this vectored thrust device comprises electrical motor 4, jet pipe 5 and jet pipe deflector 6, described electrical motor is installed in fuselage interior, the jet pipe front end connects electrical motor, jet pipe tail end 7 stretches out fuselage tail end and deflection certain angle, the described jet pipe deflector deflecting direction of adjustable jet tube tail end at any time during work, thereby control thrust direction, this jet pipe tail end is up and down deflection both, also can deflection.
In order to promote the control manoevreability of unmanned plane, described wing rear side all is hinged with aileron 8.
Principle of work of the present invention is:
This unmanned plane adopts Thrust Vectoring Technology, is the thrust direction that produces by jet pipe deflection control electrical motor, thereby obtains control torque, realizes the attitude control to unmanned plane.The characteristics of Thrust Vectoring Technology are that control torque is not subjected to the impact of the attitude of unmanned plane own by motor control, therefore, can guarantee to make low speed, large angle of attack maneuvering flight and the additional manipulation moment of utilizing thrust vectoring to provide during a few near failure of primary control surface is controlled UAV Maneuver at unmanned plane.
After unmanned plane has adopted Thrust Vectoring Technology, the up and down deflection of electrical motor jet pipe, the thrust of generation is not subjected to the impact of the center of gravity of unmanned plane, directly produces the pitching moment around the unmanned plane center of gravity, and at this moment thrust has just been brought into play the effect the same with the unmanned plane controlsurface.Because the generation of thrust only has relation with electrical motor, even if the angle of attack of unmanned plane has surpassed stalling incidence like this, thrust still can provide moment to make the unmanned plane trim, and wing can also produce enough large lift, just can guarantee that unmanned plane continues normal flight aloft.And, find also that by experiment after the thrust deflection, not only thrust can produce direct projection lift, can also make wing produce induced lift by the supercirculation effect, total lift is improved.
Thrust Vectoring Technology not only makes the manoevreability of unmanned plane greatly improve, this is because the supercirculation lift of the unmanned plane of use Thrust Vectoring Technology and thrust all is conducive to reduce unmanned plane at the component of lift direction liftoff and touchdown speed, the braking force of unmanned plane after landing also significantly improves, shorten the ground run distance of unmanned plane, significantly promoted unmanned plane and had STOL capability.
In the present patent application automatically controlled part is not described in detail.
Although disclose for the purpose of illustration embodiments of the invention and accompanying drawing, but it will be appreciated by those skilled in the art that, in the spirit and scope that do not break away from the present invention and claims, various replacements, variation and modification all are possible, therefore, scope of the present invention is not limited to embodiment and the disclosed content of accompanying drawing.
Claims (3)
1. vectored thrust type unmanned plane, comprise screw propeller, fuselage, wing and empennage, propeller coaxial is installed in the fuselage datum front end, the waist bilateral symmetry is installed wing, and the afterbody bilateral symmetry is equipped with empennage, it is characterized in that: described fuselage datum afterbody is equipped with a vectored thrust device, this vectored thrust device comprises electrical motor and jet pipe, described electrical motor is installed in fuselage interior, and the jet pipe front end connects electrical motor, and the jet pipe tail end stretches out the fuselage tail end.
2. vectored thrust type unmanned plane according to claim 1 is characterized in that: described jet pipe tail end is by jet pipe deflector control rotation angle.
3. vectored thrust type unmanned plane according to claim 1, it is characterized in that: described wing rear side all is hinged with aileron.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105582245A CN103010458A (en) | 2012-12-19 | 2012-12-19 | Vectored thrust type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105582245A CN103010458A (en) | 2012-12-19 | 2012-12-19 | Vectored thrust type unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN103010458A true CN103010458A (en) | 2013-04-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012105582245A Pending CN103010458A (en) | 2012-12-19 | 2012-12-19 | Vectored thrust type unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389628A (en) * | 2020-11-24 | 2021-02-23 | 湖南翰坤实业有限公司 | Unmanned aerial vehicle |
| CN113232827A (en) * | 2021-05-19 | 2021-08-10 | 南京航空航天大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle for flight performance and multi-screen interconnected unmanned aerial vehicle formation |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1895961A (en) * | 2005-07-17 | 2007-01-17 | 张斌 | Prey-bird machine tail |
| CN101804865A (en) * | 2010-03-16 | 2010-08-18 | 北京航空航天大学 | Small multi-purpose unmanned aerial vehicle |
| WO2012064343A1 (en) * | 2010-11-12 | 2012-05-18 | Bell Helicopter Textron Inc. | Propulsive anti-torque nozzle system with external rotating sleeve for a rotorcraft |
| CN203020541U (en) * | 2012-12-19 | 2013-06-26 | 天津全华时代航天科技发展有限公司 | Vector thrust type unmanned aerial vehicle |
-
2012
- 2012-12-19 CN CN2012105582245A patent/CN103010458A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1895961A (en) * | 2005-07-17 | 2007-01-17 | 张斌 | Prey-bird machine tail |
| CN101804865A (en) * | 2010-03-16 | 2010-08-18 | 北京航空航天大学 | Small multi-purpose unmanned aerial vehicle |
| WO2012064343A1 (en) * | 2010-11-12 | 2012-05-18 | Bell Helicopter Textron Inc. | Propulsive anti-torque nozzle system with external rotating sleeve for a rotorcraft |
| CN203020541U (en) * | 2012-12-19 | 2013-06-26 | 天津全华时代航天科技发展有限公司 | Vector thrust type unmanned aerial vehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389628A (en) * | 2020-11-24 | 2021-02-23 | 湖南翰坤实业有限公司 | Unmanned aerial vehicle |
| CN113232827A (en) * | 2021-05-19 | 2021-08-10 | 南京航空航天大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle for flight performance and multi-screen interconnected unmanned aerial vehicle formation |
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Application publication date: 20130403 |